Follow-up skin mechanism of wing folding part
By designing a follow-up skin mechanism at the folding part of the aircraft wing, and using the rocker link to flip the skin to avoid the wire harness, the problem of interference between the wire harness and the skin is solved, and the integrity of the aerodynamic shape of the wing and the reduction of foreign matter entry is achieved. .
Patent Information
- Application Number
- CN202411550548.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-01
- Publication Date
- 2025-02-07
AI Technical Summary
During the folding of the aircraft wing, the wire harness may interfere with the skin. Existing solutions such as beam splitting or excision of the skin have disadvantages, which affects aerodynamic performance or increases the risk of foreign matter entry.
A follow-up skin mechanism at the folding part of the wing is designed. By installing a rocker arm connecting rod mechanism on the local skin, the skin can be flipped when the wing is folded, avoiding the sweeping path of the wire harness, thereby solving the interference problem.
No additional driving components are required, and the existing wing structure is used to add a rocker linkage mechanism to achieve follow-up between the skin and the wing, effectively avoid interference between the wire harness and the skin, ensure the integrity of the aerodynamic shape of the wing, and reduce the risk of foreign objects entering.
Smart Images
Figure CN119389420A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a follower skin mechanism of a wing folding part. Background Art
[0002] In order to save parking space, some existing advanced aircraft models need to fold their wings. When high-power electrical equipment is installed at the end of the wing of such aircraft, thicker power supply or control harnesses will be laid inside the wing. Constrained by the bending radius of the harness and the thickness of the wing, these harnesses cannot reserve enough stretch at the folding docking position when they are arranged, which may cause interference with the skin when the wing is folded. The conventional method to avoid such problems is to split the thicker harness or cut off the skin at the interfering part. Both methods have certain disadvantages: the first method is not conducive to the processing and testing of the harness, and has a limited scope of application - the high-power electrical equipment itself requires a large wire core cross-sectional area, which does not meet the current carrying capacity requirements after splitting; the second method is to partially cut off the wing skin, which will affect the aerodynamic performance of the wing when it is unfolded, and there is a risk of foreign matter entering. Summary of the invention
[0003] Purpose of the Invention
[0004] Aiming at the problem that the wiring harness may interfere with the skin during the random wing folding process, the present invention provides a follow-up skin mechanism for the wing folding part.
[0005] Inventing technical solutions
[0006] A follower skin mechanism for a wing folding portion comprises a follower cover which is an independent skin module made of a local skin that may interfere with a wiring harness, and can be turned over with the outer wing.
[0007] Preferably, the follower skin forms a complete streamline shape with the wing skin when the wing is unfolded, and when the wing is folded, the follower skin flips to a set angle to avoid the sweep path of the wire beam.
[0008] Preferably, a rocker arm connected to the follower skin is hinged to one end of a connecting rod, and the other end of the connecting rod is hinged to an outer wing that needs to perform folding movement.
[0009] Preferably, the rocker arm is arranged on a side of the moving skin close to the outer wing.
[0010] Preferably, a rotating shaft support is arranged on one side of the follower skin close to the inner wing, and the rotating shaft support is hinged to the inner wing.
[0011] Preferably, the shaft support is hinged to the follower skin shaft fixedly connected to the inner wing.
[0012] Preferably, a driving joint is fixedly connected to the outer wing, and the other end of the connecting rod is hinged to the driving joint.
[0013] Preferably, the skin rotation axis is close to the seam between the follower skin and the inner wing skin.
[0014] Preferably, the bending state of the wire harness after the outer wing is folded at a specified angle is obtained by simulation, and the local skin position that may interfere with the wire harness is determined by the simulation result.
[0015] The advantages of the present invention are: without the need for additional driving components, a set of rocker arm linkage mechanisms is added to the existing wing structure to achieve partial skin and wing follow-up, which can effectively solve the problem of interference between the wiring harness and the skin when the wing is folded. Compared with the conventional method of cutting off the skin at the interfering part, the present invention effectively ensures the integrity of the wing's aerodynamic shape, and can effectively prevent foreign matter from entering the wing from the opening, causing the folding actuating components or the control mechanism of the rudder to get stuck. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 Schematic diagram of a typical aircraft wing folded.
[0017] Figure 2 It is a schematic diagram of the bending condition of the wire harness when the wing is folded and the state of the follower skin proposed by the present invention.
[0018] Figure 3 It is a schematic diagram of the bending condition of the wire harness when the wing is unfolded and the state of the follower skin proposed by the present invention.
[0019] Figure 4 It is a schematic structural diagram of the following skin of the present invention.
[0020] In the figure: 1 inner wing front beam; 2 outer wing front beam; 3 follower skin; 4 wire harness; 5 wire harness clamp; 6 connecting rod; 7 wing folding shaft; 8 inner wing skin; 9 outer wing skin; 10 drive joint; 11 skin shaft; 12 rocker arm; 13 shaft support. DETAILED DESCRIPTION
[0021] The present invention is achieved through the following technical solutions.
[0022] A follower skin mechanism of a wing folding part mainly comprises a follower skin 3, a driving joint 10, a connecting rod 6, a rocker arm 12, a skin rotating shaft 11, and a rotating shaft support 13.
[0023] When the wing is unfolded, the follower skin 3 forms a complete streamline shape with the wing skin to maintain the overall aerodynamic performance of the aircraft; when the wing is folded, the follower skin 3 flips a certain angle to avoid the wire harness sweep path and avoid interference. The size of the follower skin 3 is determined according to the spatial position of the wire harness in the folded state.
[0024] The driving joint 10 is installed on the outer side of the wing that needs to perform folding movement, and forms a hinge structure with the end of the connecting rod 6. The driving joint 10 is generally in the form of a shaft.
[0025] The connecting rod 6 is used to connect the driving joint 10 and the rocker arm 12 on the following skin 3 to transmit the movement and force between the outer wing and the following skin 3.
[0026] The rocker arm 12 is mounted on the follower skin 3 and forms a hinge structure with the end of the connecting rod 6 to provide a driving connection structure for the follower skin 3 .
[0027] The skin shaft 11 is installed on the inner wing to provide a shaft and support for the follower skin 3. The skin shaft 11 is located as close as possible to the joint between the follower skin 3 and the inner wing skin 8 to ensure that the follower skin 3 meets the rotation angle requirements during rotation and does not interfere with the structural parts or wiring harnesses.
[0028] The rotation axis support 13 is installed on the follower skin 3 at a position corresponding to the skin rotation axis 11 , and is used to provide support for the follower skin 3 while forming an articulated motion pair with the rotation axis 6 .
[0029] Example
[0030] like Figure 1 When on the ground, the outer wing of the aircraft needs to be folded upwards 100°. When in flight, the outer wing is unfolded and in the same horizontal state as the inner wing. A high-power electrical device is installed at the end of the outer wing. The device needs to be equipped with a power supply harness 4 with an outer diameter of 25mm. The harness 4 is extended from the fuselage and fixed to the inner wing front beam 1 and the outer wing front beam 2 through the harness clamp 5 along the wing span. The minimum bending radius of the harness 4 is about 150mm.
[0031] In order to ensure that the wire harness 4 can meet the minimum bending radius requirement when the outer wing is folded upward, a certain amount of wire harness bending margin needs to be reserved between the wire harness clamps on both sides of the wing folding shaft 7 when the wire harness 4 is installed and arranged. Figure 2 .
[0032] Based on the positions of the harness clamps 5 on both sides of the wing folding shaft 7 and the harness length between the two clamps, the bending state of the harness 4 after the outer wing is folded 100° can be simulated, as shown in FIG. Figure 3 In order to avoid interference between the wiring harness 4 and the inner wing upper skin 8 in this state, the local skin that may interfere is made into a follower skin 3 that can move independently.
[0033] A rocker arm 12 is arranged on the side of the follower skin 3 close to the outer wing, and a rotating shaft support 13 is arranged on the side close to the inner wing. Both the rocker arm 12 and the rotating shaft support 13 are fixedly connected to the follower skin 3 .
[0034] To ensure that the follower skin 3 can be flipped with the outer wing, a drive joint 10 is fixed to the outer wing front beam 1, and a follower skin shaft 11 is fixed to the inner wing front beam. The follower skin shaft 11 is hinged to the shaft support 13.
[0035] In addition, a connecting rod 6 is provided between the driving joint 10 and the rocker arm 12 , and joint bearings are pressed at both ends of the connecting rod 6 , and are respectively hinged to the driving joint 10 and the rocker arm 12 .
[0036] When the outer wing turns upward around the wing folding axis 7, the driving joint 10 fixed to the outer wing front beam 1 moves upward, and drives the follower skin 3 to turn upward around the follower skin axis 11 synchronously through the connecting rod 6 and the rocker arm 12. Figure 3 The effect shown.
[0037] The protection scope of the present invention is not limited to the above-mentioned embodiments. Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the scope of the present invention. If these changes and modifications fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include these changes and modifications.
Claims
1. A follow-up skin mechanism for a wing folding portion, characterized in that: The invention comprises a follower skin (3), wherein the follower skin (3) is an independent skin module made of a local skin that may interfere with the wiring harness, and the follower skin (3) can be turned over with the outer wing.
2. A follow-up skin mechanism for a wing folding portion as claimed in claim 1, characterized in that: The follower skin (3) forms a complete streamline shape with the wing skin when the wing is in an unfolded state; and the follower skin (3) flips at a set angle to avoid the wire beam sweep path when the wing is in a folded state.
3. A follow-up skin mechanism for a wing folding portion as claimed in claim 1, characterized in that: A rocker arm (12) connected to the follower skin (3) is hinged to one end of a connecting rod (6), and the other end of the connecting rod (6) is hinged to the outer wing that needs to perform folding movement.
4. A follow-up skin mechanism for a wing folding portion as claimed in claim 3, characterized in that: The rocker arm 12 is arranged on a side of the follower skin (3) close to the outer wing.
5. A follow-up skin mechanism for a wing folding portion as claimed in claim 3, characterized in that: A rotating shaft support (13) is arranged on one side of the follower skin (3) close to the inner wing, and the rotating shaft support (13) is hinged to the inner wing.
6. A follow-up skin mechanism for a wing folding portion as claimed in claim 5, characterized in that: The rotating shaft support (13) is hinged to the follower skin rotating shaft (11) fixedly connected to the inner wing.
7. A follow-up skin mechanism for a wing folding portion as claimed in claim 5, characterized in that: A driving joint (10) is fixedly connected to the outer wing, and the other end of the connecting rod (6) is hinged to the driving joint (10).
8. A follow-up skin mechanism for a wing folding portion as claimed in claim 6, characterized in that: The skin rotation axis (11) is close to the joint between the follower skin (3) and the inner wing skin (8).
9. A follow-up skin mechanism for a wing folding portion as claimed in claim 1, characterized in that: The bending state of the wiring harness after the outer wing is folded at a specified angle is obtained by simulation, and the local skin position that may interfere with the wiring harness is determined by the simulation results.